Systems and methods for calibrating a sensor position on an aircraft

ABSTRACT

Methods and systems for calibrating aircraft position by providing touch-enabled selection of onboard sensors on an aircraft. The method includes receiving sensor map location information for onboard sensors including N position computers, a global positioning system (GPS) sensor, an inertial reference system (IRS) sensor, and a radio navigation (NAV) sensor; receiving sensor data from the onboard sensors, and configuring a user interface layout for the touch display unit presenting the onboard sensors using symbols at respective locations. Embodiments depict the sensors with intuitive symbols and provide a terrain layout in the background. The method includes interpreting a touch input from the touch-enabled display unit to select a position computer and an onboard sensor, and to calibrate the selected position computer with the selected onboard sensor and update the user interface layout to reflect the calibration, responsive to the touch input.

CROSS REFERENCE TO RELATED APPLICATION

This application claims priority to Indian Provisional PatentApplication No. 202011033342, filed Aug. 4, 2020, the entire content ofwhich is incorporated by reference herein.

TECHNICAL FIELD

The following disclosure relates generally to the selection of sensorson aircraft, and, more particularly, to systems and methods forcalibrating aircraft position by providing touch-enabled selection ofonboard sensors on an aircraft.

BACKGROUND

Modern complex avionics systems generally have a position computer thatuses multiple redundant sensor systems to automatically compute anaircraft position. In some scenarios, the crew may desire to interactwith this avionics system. In some scenarios, the crew may wish tocalibrate the position computer by including or excluding individualsensors from this computation. In these scenarios, they generally mustuse a user input device and perform a series of operations, navigatingback and forth between windows.

The windows that a crew has to navigate between may include a firstwindow with a textual readout of sensor latitude and longitude positionin a list format. Using this first window, a sensor position has to bementally processed by the crew and translated to a relative sensorposition with respect to current aircraft position and relative to otheronboard sensors to be useful. In some scenarios, the crew may haveaccess to a second window with a graphical representation of positionsof onboard sensors relative to a voted, master aircraft position,however even using this window, interacting with the system can be verycumbersome and does not provide a pilot with the ability to seepotential data changes reflected in real time as sensor selections aremade.

Accordingly, technologically improved systems and methods forcalibrating aircraft position by providing touch-enabled selection ofonboard sensors on an aircraft that provide a direct and intuitive,touch-based solution for selection of sensors and provide immediatevisual feedback are desirable. Furthermore, other desirable features andcharacteristics of the present invention will be apparent from thesubsequent detailed description and the appended claims, taken inconjunction with the accompanying drawings and the foregoing technicalfield and background.

BRIEF SUMMARY

This summary is provided to describe select concepts in a simplifiedform that are further described in the Detailed Description. Thissummary is not intended to identify key or essential features of theclaimed subject matter, nor is it intended to be used as an aid indetermining the scope of the claimed subject matter.

Provided is a system for calibrating aircraft position by providingtouch-enabled selection of onboard sensors on an aircraft having atouch-enabled display unit, the system includes: a number N of positioncomputers, N being greater than or equal to 1; a plurality of onboardsensors for providing respective sensor data, the onboard sensorsincluding a global position system (GPS) sensor, an inertial referencesystem (IRS) sensor, a radio navigation (NAV) sensor, and, for each ofthe N Position computers, a respective FMS sensor; a controller circuitcomprising a processor configured to execute programming instructionsstored in a memory, that when executed by the processor cause thecontroller circuit to: receive sensor map location information for theonboard sensors; receive sensor data from the onboard sensors; configurea user interface layout for the touch-enabled display unit based on thesensor map location information and the sensor data, the user interfacelayout presenting the N Position computers, the GPS sensor, the IRSsensor, the NAV sensor, and the N FMS sensors, using symbols atrespective locations; render the user interface layout on thetouch-enabled display unit; interpret a touch input from thetouch-enabled display unit to select a position computer and to selectan onboard sensor; calibrate the selected Position computer with theselected onboard sensor responsive to the touch input; modify the userinterface layout to reflect the calibration; and modify a displayedrange ring on the user interface layout responsive to the calibration.

Also provided is a processor-implemented method for calibrating anaircraft position on an aircraft having a touch-enabled display unit.The method includes: receiving sensor map location information foronboard sensors, the onboard sensors including N flight managementsystem (FMS) computers, a geospatial positioning system (GPS) sensor, aninstrument radar system (IRS) sensor, a navigation (NAV) sensor, and NFMS sensors; receiving sensor data from the onboard sensors; configuringa user interface layout for the touch-enabled display unit based on thesensor map location information and the sensor data, the user interfacelayout presenting the N Position computers, the GPS sensor, the IRSsensor, the NAV sensor, and the N FMS sensors, using symbols atrespective locations; rendering the user interface layout on thetouch-enabled display unit; interpreting a touch input from thetouch-enabled display unit to select an Position computer and to selectan onboard sensor; calibrating the selected Position computer with theselected onboard sensor responsive to the touch input; modifying theuser interface layout to reflect the calibration; and modifying adisplayed range ring on the user interface layout responsive to thecalibration.

In another embodiment, a system for calibrating an aircraft position isprovided. The system includes: a configuration module operating onboardthe aircraft and configured to receive ownship data from ownship datasources including sensor data from a plurality of onboard sensors.Non-limiting examples of the onboard sensors include a global positionsystem (GPS) sensor, an inertial reference system (IRS) sensor, and, aradio navigation (NAV) sensor, and reference sensor map locationinformation for the onboard sensors to generate therefrom a userinterface layout for a touch-enabled display; a user inputinterpretation module operating on the aircraft and configured toprocess user input at the touch-enabled display with respect to the userinterface layout to: determine when a user has selected an Positioncomputer; and determine when the user has selected an onboard sensor;and a calibration module operating on the aircraft and configured tocalibrate the selected Position computer with the selected onboardsensor; and a layout modification module operating on the aircraft andoperating to determine which aspects of the user interface layout tomodify and modify the user interface accordingly, responsive to thecalibration of the Position computer with the selected onboard sensor.

Furthermore, other desirable features and characteristics of the systemand method will become apparent from the subsequent detailed descriptionand the appended claims, taken in conjunction with the accompanyingdrawings and the preceding background.

BRIEF DESCRIPTION OF THE DRAWINGS

At least one example of the present invention will hereinafter bedescribed in conjunction with the following figures, wherein likenumerals denote like elements, and:

FIG. 1 is a block diagram of a system for calibrating an aircraftposition by providing touch-enabled selection of onboard sensors on anaircraft, as illustrated in accordance with an exemplary embodiment ofthe present disclosure;

FIG. 2 is an architectural block diagram of one or more process modulesin the system for calibrating an aircraft position by providingtouch-enabled selection of onboard sensors on an aircraft, in accordancewith an exemplary embodiment of the present disclosure;

FIGS. 3-14 depict various presentations of information on a graphicaluser interface layout for a touch display unit, in accordance with anexemplary embodiment of the present disclosure; and

FIG. 15 is a flow chart of a method for calibrating an aircraft positionby providing touch-enabled selection of onboard sensors on an aircraft,as may be implemented by the system of FIG. 1, in accordance with anexemplary embodiment of the present disclosure.

DETAILED DESCRIPTION

The following Detailed Description is merely exemplary in nature and isnot intended to limit the invention or the application and uses of theinvention. The term “exemplary,” as appearing throughout this document,is synonymous with the term “example” and is utilized repeatedly belowto emphasize that the description appearing in the following sectionmerely provides multiple non-limiting examples of the invention andshould not be construed to restrict the scope of the invention, asset-out in the Claims, in any respect. As further appearing herein, theterm “pilot” encompasses all users of the below-described aircraftsystem.

As mentioned, in modern avionics systems, generally a position computeruses multiple redundant sensor systems to automatically compute anaircraft position. In scenarios, the crew desires to calibrate theposition computer by including or excluding individual sensors from thiscomputation. In these scenarios, they generally must use a user inputdevice and perform a series of operations, navigating back and forthbetween windows. The human-machine interface that they must interactwith for this calibration generally includes a user input device, suchas a keyboard, and a separate display device, and the human-machineinteraction includes a series of cumbersome operations, navigating backand forth between windows, during which time the human-machine interfaceis not providing a pilot with the ability to see potential data changesreflected in real time as sensor selections are made.

The embodiments described herein deliver technologically improvedsystems and methods for calibrating a sensor position on an aircrafthaving a touch-enabled display unit. Embodiments provide a direct andintuitive, touch-based solution for selection of sensors (or otherexternal references) with immediate visual feedback, including immediatesensor data position updates, in a What You See Is What You Get(WYSIWYG) presentation style. Specifically, embodiments provide a visualdepiction of individual position sensors distributed such that theirposition on a lateral display represents their position relative to theposition of the aircraft. Other words, it is like having a map with aposition of own ship and position of individual sensors. Accordingly,the described embodiments deliver an objectively improved human-machineinterface during sensor calibration that reduces cognitive load for theflight crew.

FIG. 1 is a block diagram of a system 102 for calibrating a sensorposition on an aircraft having a touch-enabled display unit, asillustrated in accordance with an exemplary and non-limiting embodimentof the present disclosure. The system 102 for computing an aircraftposition by providing touch-enabled selection of onboard sensors (118,120, 122, 124 may be utilized onboard a mobile platform 100 to providean aircraft position (shortened herein to “system” 102), as describedherein. In various embodiments, the mobile platform is an aircraft 100,which carries or is equipped with the system 102. As schematicallydepicted in FIG. 1, system 102 includes the following components orsubsystems, each of which may assume the form of a single device ormultiple interconnected devices: a controller circuit 104 operationallycoupled to: at least one display device 110; computer-readable storagemedia or memory 132; an optional input interface 114, and ownship datasources 106. The system 102 may be separate from or integrated within: aflight management system (FMS) and/or a flight control system (FCS). Thesystem 102 may also contain a datalink subsystem including an antenna54, which may wirelessly transmit data to and receive real-time data andsignals from various external sources (52), including, each of: traffic,air traffic control (ATC), weather systems, ground stations, and thelike.

Although schematically illustrated in FIG. 1 as a single unit, theindividual elements and components of the system 102 can be implementedin a distributed manner utilizing any practical number of physicallydistinct and operatively interconnected pieces of hardware or equipment.When the system 102 is utilized as described herein, the variouscomponents of the system 102 will typically all be located onboard theAircraft 100.

The terms “controller circuit,” and “module,” as appearing herein,broadly encompass those components utilized to carry-out or otherwisesupport the processing functionalities of the system 102. Accordingly,controller circuit 104 and modules of FIG. 2 can encompass or may beassociated with a programmable logic array, application specificintegrated circuit or other similar firmware, as well as any number ofindividual processors, flight control computers, navigational equipmentpieces, computer-readable memories (including or in addition to memory132), power supplies, storage devices, interface cards, and otherstandardized components. In various embodiments, controller circuit 104embodies one or more processors operationally coupled to data storagehaving stored therein at least one firmware or software program(generally, computer-readable instructions that embody an algorithm) forcarrying-out the various process tasks, calculations, andcontrol/display functions described herein. During operation, thecontroller circuit 104 may be programmed with and execute the at leastone firmware or software program, for example, program 134 withpreprogrammed variables 136, that embodies an algorithm for calibratinga sensor position on an aircraft having a touch-enabled display unit, tothereby perform the various process steps, tasks, calculations, andcontrol/display functions described herein.

In various embodiments, the controller circuit 104 may utilize acommunications circuit 140 to exchange data, including real-timewireless data, with one or more external sources 52 to support operationof the system 102. In various embodiments, the communications circuit140 manages bidirectional wireless data exchange over a communicationsnetwork, such as a public or private network implemented in accordancewith one or more communication protocols. An example communicationprotocol is a Transmission Control Protocol/Internet Protocolarchitectures or other conventional protocol standards. In variousembodiments, the communications circuit 140 manages encryption andmutual authentication techniques, as appropriate, to ensure datasecurity.

Memory 132 is a data storage that can encompass any number and type ofstorage media suitable for storing computer-readable code orinstructions, such as the aforementioned software program 134, as wellas other data generally supporting the operation of the system 102.Memory 132 may also store preprogrammed variables, such as one or morethreshold values, for use by an algorithm embodied in software program134. Various embodiments also employ one or more database(s) 50, anotherform of storage media that may be integrated with memory 132 or separatefrom it.

In various embodiments, aircraft-specific parameters and information foraircraft 100 may be stored in the memory 132 or in a database 50 andreferenced by the program 134. Non-limiting examples ofaircraft-specific information includes sensor map location informationfor all available onboard sensors, and the like. As used herein, thesensor map location information includes, for each available onboardsensor used for navigation, a sensor category and sensor location.

In various embodiments, a symbol library (described in connection withFIG. 13) might be predefined and stored in the database 50 or in thememory 132.

In various embodiments, two- or three-dimensional terrain and map datamay be stored in a database 50, including airport features data,geographical (terrain), buildings, bridges, and other structures, streetmaps, and navigational databases, which may be updated on a periodic oriterative basis to ensure data timeliness. This map data may be uploadedinto the database 50 at an initialization step and then periodicallyupdated, as directed by either a program 134 update or by an externallytriggered update.

Ownship data sources 106 may include system status sensors and one ormore position computers 116. In various embodiments, the positioncomputers 116 are referred to as Flight Management System (FMS)computers 116 or navigators. Ownship data sources 106 also includevarious onboard sensors used for navigation, and can be categorized.Non-limiting examples of the onboard sensor categories include GlobalPosition System (GPS) sensors 118, Inertial Reference System (IRS)sensors 120, radio Navigation (NAV) sensors 122, position sensors 124,and any other of a plurality of other position sensors. There may bemore than one onboard sensor in each category. The position sensor orFMS sensor category, is actually a derived sensor category: In practice,the position computer/FMS 116 performs an algorithm which, for eachposition computer/FMS 116, calculates a blended position using otheravailable sensors, such as IRS, GPS, Radio navigation (NAV) etc.,considering their integrity and quality, therefore, these sensors mayalso be referred to herein as a blended position sensor/FMS sensor.Therefore, there is a one to one correspondence of positioncomputers/FMSs 116 to position sensor/FMS sensors 124. Sensor dataprovided by the onboard sensors used for navigation may include locationand direction/orientation information.

Collectively, ownship data sources 106 supply various types of data ormeasurements to controller circuit 104 during aircraft flight. Invarious embodiments, the ownship data sources 106 include onboardsystems, onboard status sensors, and onboard inertial sensors.Accordingly, ownship data sources 106 collectively supply, withoutlimitation, one or more of: inertial reference system measurementsproviding a location, Flight Path Angle (FPA) measurements, airspeeddata, groundspeed data (including groundspeed direction), vertical speeddata, vertical acceleration data, altitude data, attitude data includingpitch data and roll measurements, yaw data, heading information, sensedatmospheric conditions data (including wind speed and direction data),flight track data, radar altitude data, and geometric altitude data.

In certain embodiments of system 102, the controller circuit 104 and theother components of the system 102 may be integrated within or cooperatewith any number and type of systems commonly deployed onboard anaircraft including, for example, a position sensor/FMS 116, an AttitudeHeading Reference System (AHRS), and/or an Inertial Reference System(IRS).

With continued reference to FIG. 1, display device 110 can include anynumber and type of image generating devices on which one or more avionicdisplays 112 may be produced. When the system 102 is utilized for amanned aircraft, display device 110 may be affixed to the staticstructure of the aircraft cockpit as, for example, a Head Down Display(HDD) or Head Up Display (HUD) unit. Alternatively, display device 110may assume the form of a movable display device (e.g., a pilot-worndisplay device) or a portable display device, such as an ElectronicFlight Bag (EFB), a laptop, or a tablet computer carried into theaircraft cockpit by a pilot.

At least one avionic display 112 is generated on display device 110during operation of the system 102; the term “avionic display” definedas synonymous with the term “aircraft-related display” and “cockpitdisplay” and encompasses displays generated in textual, graphical,cartographical, and other formats. The system 102 can generate varioustypes of lateral and vertical avionic displays 112 on which map viewsand symbology, text annunciations, and other graphics pertaining toflight planning are presented for a pilot to view. The display device110 is configured to continuously render at least a lateral display 112showing the aircraft 100 at its current location within the map data.

The avionic display 112 generated and controlled by the system 102 caninclude a user input interface 114, including graphical user interface(GUI) objects and alphanumerical input displays of the type commonlypresented on the screens of MCDUs, as well as Control Display Units(CDUs) generally. Specifically, embodiments of avionic displays 112include one or more two dimensional (2D) avionic displays, such as ahorizontal (i.e., lateral) navigation display or vertical navigationdisplay; and/or on one or more three dimensional (3D) avionic displays,such as a Primary Flight Display (PFD) or an exocentric 3D avionicdisplay.

In various embodiments, a human-machine interface is implemented as anintegration of the user input interface 114 and a touch-enabled displaydevice 110, for example, a touch screen display device. In someembodiments, the human-machine interface includes an integration of theuser input interface 114, a display device 110, and a user input device108, such as a keyboard, or cursor control device. Embodiments of thecontroller circuit 104 employ various display and graphics systemsprocesses to configure and render a specific user interface layout (FIG.2, 203) and command and control the display device 110 to render theuser interface layout thereon. The user interface layout 203 may includegraphical user interface (GUI) objects or elements described herein,including, for example, touch-sensitive labels, symbols, buttons,sliders, and the like, which are used to prompt a user to interact.Accordingly, the human-machine interface of the present inventionprovides user input, activates respective functions, and provides userfeedback, responsive to received user touch screen input.

Turning now to FIG. 2, and with continued reference to FIG. 1, variousembodiments of the system 102 may comprise one or more process modules,such as those shown in the architectural block diagram 200. Aconfiguration module 202 may direct the steps of processing input fromthe ownship data sources 106 and organizing the data into an avionicdisplay 112; this includes creating the user interface layout 203 forthe user input interface 114, to have the position computers and onboardsensors used for navigation represented at their respective locations,overlaid on a lateral avionic display and sized to be compatible withthe available display device 110. The configuration module 202 mayconfigure a user interface layout 203 for a touch display unit based onthe sensor map location information and the sensor data, the userinterface layout 203 presenting the N FMS computers, the GPS sensor, theIRS sensor, the radio NAV sensor, and the N FMS sensors, using symbolsat respective locations.

In embodiments that display terrain data, the configuration module 202may receive the terrain data and render a terrain layer in thebackground of the user interface layout rendered on the touch-enableddisplay unit. In embodiments that utilize specific symbols for thevarious onboard sensors, the configuration module 202 may reference apredefined and stored symbol library and use a first symbol to indicateeach global position system (GPS) sensor, a second symbol to representeach inertial reference system (IRS) sensors, and a third symbol toindicate each radio navigation (NAV) sensors; in these embodiments, anyblended position sensors on the user interface layout 203 may beindicated with an alphanumeric label, or fourth symbol. The system 102assures that the first, second, third and fourth symbols are visuallydistinguishable from each other; in an example, the first symbol, secondsymbol, third symbol, and fourth symbol include an antenna, a satellite,and a gyroscope, as shown in FIGS. 13 and 14. In various embodiments,the symbol selected to represent an onboard sensor is picked such thatit intuitively represents a sensor type so that the pilot can recognizeit without having to read text.

The system 102 renders the user interface layout on the display device110. In various embodiments, the display device 110 is a touch screendisplay device or touch-enabled display device.

A user input interpretation module 204 may direct various processes oftouch detection with respect to the display device 110. Initially, atouch may be detected in the area 310 for displaying available positioncomputers/FMSs, and the selected FMS is indicated therein. In a firstaspect, touch detection may include determining a presence/absence of afinger touch at a location on the user interface layout 203. In a secondaspect, touch detection includes detecting a continuous touch of atleast a first duration of time at an indicator of the onboard sensor onthe user interface layout 203. Additionally, touch detection mayinclude: displaying an alphanumeric message to update the selected FMScomputer with the onboard sensor upon detection of the touch input; and,determining that the onboard sensor has been selected upon meeting theconditions (i) an expiration of the first duration of time withcontinuous touch, (ii) followed by the touch ceasing.

A mapped location of a detected touch may be compared to a predefinedsensor assignment or other functional meaning on the user interfacelayout 203, as an aspect of user input interpretation. In embodimentsthat support an “add fix” feature, the user input interpretation module204 detects that the add fix button has been touch selected, receivesadditional alphanumeric input at a designated area for the fix (such asis shown in FIG. 6, area 602), and determines when a user has selectedthe fix to correlate with the position computer/FMS. The user inputinterpretation module 204 may interpret touch input from the touchdisplay unit 110 to select an onboard sensor. Output from the user inputinterpretation module 204 may include a selected position computer/FMSand a selected onboard sensor for calibration. In an embodiment, theoutput from the user input interpretation module 204 may include aselected position computer/FMS and a fix, or waypoint or other locationentered as an “add fix.”

The output from the user input interpretation module 204 is received bythe calibration module 206; the calibration module 206 operates bycalibrating the selected position computer/FMS computer according theuser input, e.g., with the selected onboard sensor responsive to thetouch input. Said differently, the calibration module 206 operates byproviding a position solution, i.e., by calibrating the positioncomputer/FMS by including or excluding individual sensors per theinterpreted user's input. The calibration process can finalize byupdating a position computer/FMS and on-board systems with the positionsolution.

A layout modification module 208 may receive, as input, the updatedflight management and/or on-board systems information, determinetherefrom which updates to depict on the user interface layout 203, andprovide this input into the display device 110, thereby modifying theuser interface layout 203 to reflect the calibration. The layoutmodification module 208 may also modify a displayed range ring on theuser interface layout 203, responsive to the calibration.

Turning now to FIGS. 3-12, illustrations of the human-machine interfaceenabled by the user interface layout 203 in various use cases areprovided, showing how the technical problem of calibrating the sensorposition for an aircraft is objectively improved by the system 102 overavailable options. In the example embodiments shown in FIGS. 3-12, thesystem 102 provides a lateral map avionics display 300 in a dedicatedarea, overlaid with a selection band 302 along the top, and a band alongthe bottom 350 for additional text and graphical objects. In otherembodiments, the location of the selection band and location of thebottom 350 band can differ, so long as their functionality is stillprovided. A compass indicator 304 is included for visual orientation,and one or more range-rings, such as the depicted 20 nautical mile rangering 306 may be rendered thereon.

An area 310 on the selection band 302 lists available positioncomputers/FMSs. A remaining area 311 lists onboard sensor categories. Inthe example, area 310 lists FMS 1, FMS 2 and FMS 3, indicating threeposition computers or FMSs. Various embodiments include a plurality ofonboard sensors for providing respective sensor data, the onboardsensors including a global position system (GPS) sensor, an inertialreference system (IRS) sensor, a radio navigation (NAV) sensor, and, foreach of the N FMS computers, a respective FMS sensor (the blendedsensors). The system 102 indicates the blended position sensorassociated with a selected position computer at a center of thededicated area and indicates a location of each of the onboard sensorsused for navigation in the dedicated area by rendering a respectivealphanumeric label and a symbol.

In the example of FIG. 3, FMS 1 is shown selected at 308, and acorresponding blended position computer sensor is indicated with F1(312) is shown in the center of the range ring 306. A GPS 1 (314) sensorand GPS 2 (314) sensor position are depicted, as are blended position F2(318), F3 (316), and the positions of radio navigation sensor N1 (320),radio navigation sensor N2 (322), and an IRS sensor (324). Alphanumericlabels are used for onboard sensors in this embodiment. An alphanumericposition 326 is provided for the selected FMS 1 308. An add fix buttonis rendered at 328. An observer may also note that a diamond symbol isused to indicate position sensors that are on-board (F1, G1, and G2),while an arrow symbol is used to depict position sensors that areoff-board; the arrow points in the direction of the sensor location. Forexample, position sensor N1 (320) points down and to the right, which,based on the compass indicator 304, is south by southeast.

Using FIG. 3 as the starting point, we move to FIG. 4. In FIG. 4, a userwishes to update the FMS 1 with the position of the IRS sensor (324). InFIGS. 4, 324 and 318 are near each other on the displayed area, so whenthe user touches the screen, the human-machine interface provided by thesystem 102 will prompt the user with visual feedback in the form of atext box 402 having both “update with IRS position” 404 and “update withF2 position” 406 text. The user is prompted by these options to slide afinger to select one of the options. In this example, the user slidesthe finger to highlight the “update with IRS position” text, upondetecting the selection (the processes of the user input interpretationmodule 204, including the presence/absence and duration of continuoustouch requirements are confirmed), resulting in additional visualfeedback on the human-machine interface: the position of the selectedsensor is displayed 408, and the distance to the selected sensorposition is displayed 410. The system 102 determines that selection iscomplete when, after meeting the selection requirements, the user ceasestouching the selected item. When selection is complete, the processes ofthe calibration module 206 and layout modification module 208 areperformed, and FIG. 5 depicts the F1/IRS update at the center of therange ring 306.

As mentioned, the user may wish to add a fix, and can use the “add fix”button 328 for this function. In FIG. 6, a user-friendly text box 702may open to prompt the user to enter the fix. In the example, the userhas entered a waypoint KPHX at 702 and the system 102 automaticallydisplays the position of the added fix at 704. Once the new fix has beenadded, the user can add (706) or cancel (708) the fix with selectableboxes on the interface. Once the user has added the fix, the system 102updates the interface layout to depict the position of the fix. The usermay choose to update the position computer with the newly added fix byselecting it the same way as described above: touching the userinterface at the KPHX 802 location, and holding the touch continuouslyto meet a threshold requirement, until an option for “update with KPHXposition” is displayed on the interface. When the finger slides over the“update with KPHX position,” and releases, the system 102 determinesthat it has been selected and performs the update operation as before.FIG. 9 shows this update (902), note that the distance is updated to 9.6nautical miles (904).

FIG. 10 provides an illustration of selecting the second positioncomputer, or FMS 2 (1002). As a result of this selection, the userinterface layout 203 has been modified to place the blended F2 in thecenter of the range ring 306, and the remaining available sensorpositions are depicted with respect to F2 (1004). FIG. 11 provides anillustration of selecting the third position computer, or FMS 3 (1102).As a result of this selection, the user interface layout 203 has beenmodified to place the blended F3 in the center of the range ring 306,and the remaining available sensor positions are depicted with respectto F3 (1004). FIG. 12 is included in this example to show that when auser selects FMS 1 again (1202), after the sequence illustrated by FIGS.3-11, the blended sensor position F1/KPHX (1204) is displayed, becausethat reflects the most recent user modification to FMS 1. Had the usermodified FMS2 and/or FMS 3, upon selecting them again, the most recentupdate would show there as well.

As mentioned above, in some embodiments, the system 102 may indicate theposition of each sensor by a symbol that is associated with thenavigation category of the sensor. In FIG. 13, the ownship aircraft 100is shown in the center of a couple of concentric range rings in alateral display area. An antenna symbol 1302, a gyroscope symbol 1304,and a satellite symbol 1306 is depicted.

In another mentioned embodiment, terrain data may be received, and aterrain layer may be rendered in the background of the user interfacelayout 203 rendered on the touch-enabled display unit. By adding theterrain map layer to the user interface layout 203 on the avionicsdisplay 112, the use is objectively assisted in correlating an onboardsensor position with geographical features such as lakes, curvature ofshore, mountains and curvature of the terrain, cities, rivers, and thelike. By providing this terrain map layer, it is much easier and moreintuitive for the crew to correctly pick or exclude onboard sensors frombeing considered in blended or voted position sensor calibrationcomputations.

While not depicted in FIG. 14, it is to be appreciated that theselection band 302 along the top, and the band along the bottom 350 foradditional text and graphical objects is present along with the lateraldisplay areas depicted in FIGS. 13 and 14.

Turning now to FIG. 15, the system 102 described above may beimplemented by a processor-executable method 1500 for

computing an aircraft position by providing touch-enabled selection ofonboard sensors (118, 120, 122, 124) may be utilized onboard a mobileplatform 100 to provide an aircraft position (shortened herein to method1500). For illustrative purposes, the following description of method1500 may refer to elements mentioned above in connection with FIGS. 1-2.In practice, portions of method 1500 may be performed by differentcomponents of the described system. It should be appreciated that method1500 may include any number of additional or alternative tasks, thetasks shown in FIG. 15 need not be performed in the illustrated order,and method 1500 may be incorporated into a more comprehensive procedureor method having additional functionality not described in detailherein. Moreover, one or more of the tasks shown in FIG. 15 could beomitted from an embodiment of the method 1500 as long as the intendedoverall functionality remains intact.

At 1502, the system 102 is initialized. Initialization may includeloading instructions and program 134 into a processor within thecontroller circuit 104, as well as, depending on the embodiment, loadingmap data, aircraft-specific features, and a symbol library into one ormore database(s) 50. At 1504 the sensor map location information for theaircraft is received. At 1506, the sensor data is received for theonboard sensors used for navigation. At 1508, the user interface layoutis configured. At 1510, the user interface layout 203 is rendered on atouch enabled display device. At 1512, the method performs touchinterpretation and provides related visual feedback. At 1514 theselected position computer is calibrated with a selected onboard sensor,and at 1516 the user interface layout 203 is modified accordingly. After1516, the method may end or return to 1506.

Thus, enhanced systems and methods for calibrating an aircraft positionby providing touch-enabled selection of onboard sensors on an aircrafthaving a touch-enabled display unit. The provided methods and systemsprovide an objectively improved human-machine interface with map views,intuitive symbols for onboard sensors, and notifications that providerelevant and time-critical information. The provided enhanced featuresdo not require the pilot to refer back and forth between screens or doany mental distance or location calculations.

Although an exemplary embodiment of the present disclosure has beendescribed above in the context of a fully-functioning computer system(e.g., system 102 described above in conjunction with FIG. 1), thoseskilled in the art will recognize that the mechanisms of the presentdisclosure are capable of being distributed as a program product (e.g.,an Internet-disseminated program or software application) and, further,that the present teachings apply to the program product regardless ofthe particular type of computer-readable media (e.g., hard drive, memorycard, optical disc, etc.) employed to carry-out its distribution.

Terms such as “comprise,” “include,” “have,” and variations thereof areutilized herein to denote non-exclusive inclusions. Such terms may thusbe utilized in describing processes, articles, apparatuses, and the likethat include one or more named steps or elements but may further includeadditional unnamed steps or elements. While at least one exemplaryembodiment has been presented in the foregoing Detailed Description, itshould be appreciated that a vast number of variations exist. It shouldalso be appreciated that the exemplary embodiment or exemplaryembodiments are only examples, and are not intended to limit the scope,applicability, or configuration of the invention in any way. Rather, theforegoing Detailed Description will provide those skilled in the artwith a convenient road map for implementing an exemplary embodiment ofthe invention. Various changes may be made in the function andarrangement of elements described in an exemplary embodiment withoutdeparting from the scope of the invention as set-forth in the appendedClaims.

What is claimed is:
 1. A system for calibrating aircraft position byproviding touch-enabled selection of onboard sensors on an aircrafthaving a touch-enabled display unit, the system comprising: a number Nof position computers, N being greater than or equal to 1; a pluralityof onboard sensors for providing respective sensor data, the onboardsensors including a global position system (GPS) sensor, an inertialreference system (IRS) sensor, a radio navigation (NAV) sensor, and, foreach of the N Position computers, a respective FMS sensor; a controllercircuit comprising a processor configured to execute programminginstructions stored in a memory, that when executed by the processorcause the controller circuit to: receive sensor map location informationfor the onboard sensors; receive sensor data from the onboard sensors;configure a user interface layout for the touch-enabled display unitbased on the sensor map location information and the sensor data, theuser interface layout presenting the N Position computers, the GPSsensor, the IRS sensor, the NAV sensor, and the N FMS sensors, usingsymbols at respective locations; render the user interface layout on thetouch-enabled display unit; interpret a touch input from thetouch-enabled display unit to select a Position computer and to selectan onboard sensor; calibrate the selected Position computer with theselected onboard sensor responsive to the touch input; modify the userinterface layout to reflect the calibration; and modify a displayedrange ring on the user interface layout responsive to the calibration.2. The system of claim 1, wherein to interpret the touch input includesdetecting a continuous touch of at least a first duration of time at anindicator of the onboard sensor on the user input interface.
 3. Thesystem of claim 2, wherein to interpret the touch input the controllercircuit is further configured to: display an alphanumeric message toupdate the selected Position computer with the onboard sensor upondetection of the touch input; and determine that the onboard sensor hasbeen selected upon (i) an expiration of the first duration of time withcontinuous touch, and (ii) followed by the touch input ceasing.
 4. Thesystem of claim 1, wherein the GPS sensor is a first GPS sensor, andfurther comprising a second GPS sensor.
 5. The system of claim 1,wherein the IRS sensor is a first IRS sensor, and further comprising asecond IRS sensor.
 6. The system of claim 1, wherein the NAV sensor is afirst NAV sensor, and further comprising a second NAV sensor.
 7. Thesystem of claim 1, wherein the user interface layout includes: adedicated area; and wherein the controller circuit is further configuredto: indicate a blended FMS sensor associated with the selected Positioncomputer at a center of the dedicated area; and indicate, in thededicated area, a location of each of the onboard sensors by rendering arespective alphanumeric label and a symbol.
 8. The system of claim 1,wherein the controller circuit is further configured to use a firstsymbol to indicate each global position system (GPS) sensor, a secondsymbol to represent each inertial reference system (IRS) sensor, a thirdsymbol to indicate each navigation (NAV) sensor, and a fourth symbol foreach FMS sensor, and wherein the first, second, third and fourth symbolsare visually distinguishable from each other.
 9. The system of claim 8,wherein the first symbol, second symbol, third symbol, and fourth symbolinclude an antenna, a satellite, and a gyroscope.
 10. The system ofclaim 1, wherein the controller circuit is further configured to:receive terrain data; and render a terrain layer in a background of theuser interface layout rendered on the touch-enabled display unit.
 11. Aprocessor-implemented method for calibrating an aircraft position on anaircraft having a touch-enabled display unit, the method comprising:receiving sensor map location information for onboard sensors, theonboard sensors including N flight management system (FMS) computers, ageospatial positioning system (GPS) sensor, an instrument radar system(IRS) sensor, a navigation (NAV) sensor, and N FMS sensors; receivingsensor data from the onboard sensors; configuring a user interfacelayout for the touch-enabled display unit based on the sensor maplocation information and the sensor data, the user interface layoutpresenting the N Position computers, the GPS sensor, the IRS sensor, theNAV sensor, and the N FMS sensors, using symbols at respectivelocations; rendering the user interface layout on the touch-enableddisplay unit; interpreting a touch input from the touch-enabled displayunit to select a Position computer and to select an onboard sensor;calibrating the selected Position computer with the selected onboardsensor responsive to the touch input; modifying the user interfacelayout to reflect the calibration; and modifying a displayed range ringon the user interface layout responsive to the calibration.
 12. Themethod of claim 11, further comprising: using a first symbol to indicateeach global position system (GPS) sensor, a second symbol to representeach inertial reference system (IRS) sensor, a third symbol to indicateeach navigation (NAV) sensor, and a fourth symbol for each FMS sensor;and wherein the first, second, third and fourth symbols are visuallydistinguishable from each other.
 13. The method of claim 12, wherein thefirst symbol, second symbol, third symbol, and fourth symbol include anantenna, a satellite, and a gyroscope.
 14. The method of claim 13,further comprising: receiving terrain data; and rendering a terrainlayer in a background of the user interface layout on the touch-enableddisplay unit.
 15. The method of claim 14, further comprising: detectinga continuous touch of at least a first duration of time at an indicatorof the onboard sensor on the user input interface.
 16. The method ofclaim 15, further comprising: displaying an alphanumeric message toupdate the selected Position computer with the onboard sensor upondetection of the touch input; and determining that the onboard sensorhas been selected upon (i) an expiration of the first duration of timewith continuous touch, and (ii) followed by the touch input ceasing. 17.A system for calibrating an aircraft position, comprising: a controllercircuit, the controller circuit configured to: receive ownship data fromownship data sources including sensor data from a plurality of onboardsensors, the onboard sensors including a global position system (GPS)sensor, an inertial reference system (IRS) sensor, and, a radionavigation (NAV) sensor, and reference sensor map location informationfor the onboard sensors to generate therefrom a user interface layoutfor a touch-enabled display; process user input at the touch-enableddisplay with respect to the user interface layout to: determine when auser has selected a Position computer; determine when the user hasselected an onboard sensor; calibrate the selected Position computerwith the selected onboard sensor; determine which aspects of the userinterface layout to modify; and modify (i) the user interface and (ii) adisplayed range ring on the user interface layout accordingly,responsive to the calibration of the Position computer with the selectedonboard sensor.
 18. The system of claim 17, wherein the controllercircuit is further configured to: detect a continuous touch of at leasta first duration of time at an indicator of the selected onboard sensoron the user interface layout; display an alphanumeric message to updatethe selected Position computer with the onboard sensor upon detection ofthe touch input; and determine that the onboard sensor has been selectedupon (i) an expiration of the first duration of time with continuoustouch, and (ii) followed by the touch ceasing.
 19. The system of claim18, wherein the controller circuit is further configured to: detect thatan add fix button has been touch selected; receive alphanumeric input ata designated area for a fix; and determine when the user has selectedthe fix to correlate with the selected Position computer.
 20. The systemof claim 19, wherein controller circuit is further configured to:receive terrain data; and render a terrain layer in a background of theuser interface layout rendered on the touch-enabled display unit.